Device for the injection of fuel into the flow wake of swirler vanes

Abstract

A device for the injection of fuel into the combustion chamber of a gas turbine includes at least one swirler ( 1 ) arranged in an air path with at least one swirler vane ( 2 ) and with at least one fuel injection nozzle ( 3 ), wherein the fuel injection nozzle ( 3 ) is arranged in a wake area of the swirler vane ( 2 ) and is separate from the swirler vane ( 2 ).

1. A device for the injection of fuel into the combustion chamber of a gas turbine having at least one swirler arranged in an air path with at least one swirler vane and at least one fuel injection nozzle, wherein the swirler vane has a trailing edge that is contoured, and the fuel injection nozzle is positioned separately from the swirler vane on a sidewall of the swirler in a wake area of the swirler vane near the trailing edge, the nozzle positioned to inject fuel generally in a same direction as the contoured portion of the trailing edge near the sidewall of the swirler. 
   
   
     2. A device in accordance with  claim 1 , wherein the fuel injection nozzle is positioned in an area of the air path between boundary layers of opposing sides of the swirler vane. 
   
   
     3. A device in accordance with  claim 2 , wherein the trailing edge of the swirler vane is tapered in a direction of air flow. 
   
   
     4. A device in accordance with  claim 3 , wherein the swirler vane has a contoured cross-section. 
   
   
     5. A device in accordance with  claim 4 , wherein the trailing edge of the swirler vane has a greater width in its root area than in its tip area. 
   
   
     6. A device in accordance with  claim 1 , wherein the fuel injection nozzle is positioned in an area of the air path between boundary layers of opposing sides of the swirler vane. 
   
   
     7. A device in accordance with  claim 6 , wherein the trailing edge of the swirler vane is tapered in a direction of air flow. 
   
   
     8. A device in accordance with  claim 1 , wherein the trailing edge of the swirler vane is tapered in a direction of air flow. 
   
   
     9. A device in accordance with  claim 1 , wherein the swirler vane has a contoured cross-section. 
   
   
     10. A device in accordance with  claim 9 , wherein the trailing edge of the swirler vane has a greater width in its root area than in its tip area. 
   
   
     11. A device in accordance with  claim 1 , wherein the trailing edge of the swirler vane has a greater width in its root area than in its tip area. 
   
   
     12. A device in accordance with  claim 1 , wherein the trailing edge of the swirler vane has a recessed portion near the sidewall extending upstream from a position on the trailing edge radially distant from the sidewall to a position on the trailing edge radially near the sidewall and the fuel nozzle is positioned below this recessed portion. 
   
   
     13. A device in accordance with  claim 2 , wherein the trailing edge of the swirler vane has a recessed portion near the sidewall extending upstream from a position on the trailing edge radially distant from the sidewall to a position on the trailing edge radially near the sidewall and the fuel nozzle is positioned below this recessed portion. 
   
   
     14. A device in accordance with  claim 4 , wherein the trailing edge of the swirler vane has a recessed portion near the sidewall extending upstream from a position on the trailing edge radially distant from the sidewall to a position on the trailing edge radially near the sidewall and the fuel nozzle is positioned below this recessed portion. 
   
   
     15. A device in accordance with  claim 6 , wherein the trailing edge of the swirler vane has a recessed portion near the sidewall extending upstream from a position on the trailing edge radially distant from the sidewall to a position on the trailing edge radially near the sidewall and the fuel nozzle is positioned below this recessed portion. 
   
   
     16. A device in accordance with  claim 7 , wherein the trailing edge of the swirler vane has a recessed portion near the sidewall extending upstream from a position on the trailing edge radially distant from the sidewall to a position on the trailing edge radially near the sidewall and the fuel nozzle is positioned below this recessed portion. 
   
   
     17. A device in accordance with  claim 8 , wherein the trailing edge of the swirler vane has a recessed portion near the sidewall extending upstream from a position on the trailing edge radially distant from the sidewall to a position on the trailing edge radially near the sidewall and the fuel nozzle is positioned below this recessed portion. 
   
   
     18. A device in accordance with  claim 11 , wherein the trailing edge of the swirler vane has a recessed portion near the sidewall extending upstream from a position on the trailing edge radially distant from the sidewall to a position on the trailing edge radially near the sidewall and the fuel nozzle is positioned below this recessed portion. 
   
   
     19. A device for the injection of fuel into the combustion chamber of a gas turbine having at least one swirler arranged in an air path with at least one swirler vane and at least one fuel injection nozzle, wherein a trailing edge of the swirler vane has a recessed portion near a sidewall of the swirler extending upstream from a position on the trailing edge radially distant from the sidewall to a position on the trailing edge radially near the sidewall and the fuel nozzle is positioned separately from the swirler vane below this recessed portion in a wake area of the swirler vane. 
   
   
     20. A device in accordance with  claim 19 , wherein the fuel injection nozzle is positioned to inject fuel generally in a same direction as the contoured portion of the trailing edge near the sidewall of the swirler.